模糊PID控制的惯性稳定回路

模糊控制可有效提高惯稳回路的控制精度。由于实际的惯稳模型对模糊信号响应不足,可对控制对象的输入信号u(k)进行适当放大以加快系统输出的响应速度。对传统PID与模糊PID控制的仿真研究结果表明,模糊自适应PID控制对惯稳回路的控制效果要明显优于传统PID,不仅几乎不存在超调量,而且tr、ts非常理想,因此模糊PID控制完全有可能应用于实际的惯稳回路。     

模糊推理在舰艇防空指挥系统中的应用

针对舰艇防空作战中遇到的不确定性问题,在科学分析影响目标状况因素的基础上,根据专家经验,运用模糊推理的原理和方法,重点分析了目标状况知识信息的表示方法,给出了模糊推理规则,研究设计了用于舰艇防空辅助决策的模糊专家系统。最后给出了一个应用实例。     

基于模糊逻辑和证据理论的故障诊断方法

针对故障诊断过程中信息损失的问题和D-S证据理论在处理模糊信息时的局限性,在模糊逻辑的基础上,将决策级信息融合技术应用于故障诊断系统中,提出了一种基于模糊逻辑和D-S证据理论相结合的多传感器信息融合综合故障诊断方法。该方法以模糊隶属函数来实现基本可信度分配,充分利用各种传感器的冗余和互补信息,可显著提高故障诊断的准确率,实例验证了该方法的合理性和有效性。     

影响高寒山地作战效能的气象环境模糊推理评估模型

高寒山地作战将是我军在西北方向的主要作战形式,而气象环境严重制约其作战效能的发挥。针对高寒山地典型作战样式进行研究,探讨西北地区气象环境与作战单元和作战样式的影响,并由此提炼评估模型的模糊推理规则,构建模糊推理框架,采用多级评估决策的思想和模糊逻辑推理系统,建立影响高寒山地作战的气象环境效能三级模糊推理评估模型。经试验仿真检验,其评估结果与客观实际基本相符,对高寒山地作战效能和武器作战性能的充分发挥以及最大限度利用战场气象环境优势,具有重要军事价值。     

基于目标威胁规则的雷达情报按需分发

针对预警监视网络中信息过载的问题,为了提高情报分发的效率,提出了基于目标威胁规则的情报按需分发方法。依据目标特征以及保卫对象,利用模糊综合决策和层次分析法估计目标威胁值,在此基础上,通过设定阈值过滤,并与用户作战需求模型动态匹配,最终将所得到的目标情报信息分发给特定情报用户。仿真表明,该方法能够有效地实现情报的按需分发。     

Supercritical carbon dioxide as a new working medium for pneumatic launch: A theoretical study

Compared with the conventionally gaseous or liquid working media, the specific internal energy of supercritical carbon dioxide (SCD) is higher at the same temperature and pressure, and the critical temperature of carbon dioxide is close to room temperature, making SCD a potential new working medium for pneumatic launch. To analyze the feasibility of this conception, an analytical model of a pneumatic catapult is established on basis of the conservations of mass and energy. The model consists of a high-pressure chamber and a low-pressure chamber connected by multiple valves, and there is a movable piston in the low-pressure chamber that can push an aircraft to accelerate. The effects of the launch readiness state of SCD in the high-pressure chamber, the initial volume of the low-pressure chamber and the valve control on the movement of the aircraft are analyzed. It is found that there is a restrictive relation between the temperature and pressure of the launch readiness state of SCD, i.e., there is a maximum allowable launch readiness pressure when the launch readiness temperature is fixed. If this restrictive relation is not satisfied, the working medium in the low-pressure chamber will drop to its triple point within a few milliseconds, leading to a launch failure. Owing to this restrictive relation, there is an optimal launch readiness state of SCD with the highest working capacity for any allowable launch readiness temperature. The pressure of the low-pressure chamber will decrease significantly as the initial volume increases, leading to a decreased acceleration of the aircraft. The ac-celeration can be controlled below a critical value by a designed sequential blasting technique of multiple valves. The calculated results show that a 500 kg aircraft can be accelerated from 0 to 58 m/s in 0.9 s with 36 kg of carbon dioxide. This research provides a new technique for the controllable cold launch of an aircraft.